Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. The pressure and suction side walls surround an airfoil cavity and provide an exterior airfoil surface. A baffle is arranged in the airfoil cavity and includes a supply hole. Ribs extend between at least one of the pressure and suction side walls into the airfoil cavity to support the baffle relative to the at least one of the pressure and suction side walls. The ribs are configured to provide a serpentine cooling passage between the baffle and at least one of the pressure and suction side walls. The serpentine cooling passage has first and second passes joined by a bend. The ribs form a film cooling cavity between the first and second passes. The supply hole fluidly connects the baffle to the film cooling cavity. Film cooling holes extend through the at least one of the pressure and suction side walls. The film cooling holes are in fluid communication with the film cooling cavity.

Abstract: Near-infrared shielding includes a glass material. The shielding provides transmittance at wavelengths between 390 to 700 nm, but near infrared absorbing species are distributed throughout the glass material and the shielding blocks light in the near infrared range. Further, the glass material has a near zero or negative coefficient of thermal expansion, allowing the glass material to heat up when the shielding is blocking a near infrared laser, without expanding much.

Abstract: A method of forming a component includes the steps of placing a core into a mold and pouring a component material around the core. The component material is allowed to solidify. The core is then removed from within the material, leaving a component having at least a first and a second cavity formed by the core. A first filler material is moved into the first cavity, and a second filler material is moved into the second cavity. The component is inspected for the presence of an apparent residual core within the first cavity and the second cavity. The location is identified of the apparent residual core from the core based upon an identification of whether the location of the apparent residual core is in the first or second filler materials. A method of inspecting a component formed by investment casting is also disclosed.

Abstract: A cooling device for a gas turbine engine component comprises a gas turbine engine component having an upstream channel and a downstream channel that define a cooling flow path. A meter feature includes at least one hole to meter flow from the upstream channel to the downstream channel, and has an upstream side and a downstream side. An exit diffuser extends outwardly from the downstream side of the meter feature to control flow in a desired direction into the downstream channel. A gas turbine engine is also disclosed.

Abstract: Introduced here are pressure-mitigation apparatuses for mitigating the pressure applied to a human body by the support surface of an object. The pressure-mitigation apparatus can include a series of chambers that can be individually controlled to vary the pressure therein. By varying the chamber pressure, the main point of pressure applied by the support surface to the human body may be moved across the surface of the human body. An attachment apparatus may be used to securely adhere the pressure-mitigation apparatus to the support surface.

Abstract: Provided are a program management system, a spatial management system, a data management system, and a user interface. The program management system receives contact information and a search criteria for a locate request. The program management system transmits the search criteria to the spatial management system. The spatial management system geocodes the search criteria and retrieves map data from the data management system corresponding to the search criteria geocode. The spatial management system transmits the map data to the program management system. The program management system transmits the map data to the user system and, in return, receives an indication of a site location where the operation is to be performed. The program management system transmits the site location indication to the spatial management system. The spatial management system geocodes the site location indication and transmits the site location geocode to the program management system.

Abstract: An airfoil for a gas turbine engine includes an airfoil including spaced apart pressure and suction side walls joined at leading and trailing edges to provide an exterior airfoil surface that extends in a radial direction from a platform to a tip. A cavity is provided between the pressure and suction side walls near the trailing edge. The cavity includes an interior region bounded by first and second exit regions arranged at angle relative to one another. The first and second exit regions are respectively in low and high pressure regions relative to one another. First and second pedestal groups respectively are arranged at the first and second exit regions. The second pedestal group has first and second pedestals each terminating in an end. The ends of the second pedestals extend beyond the ends of first pedestals.

Abstract: Provided are cyclic peptide analogs, conjugates comprising such compounds, and pharmaceutical compositions comprising such compounds and conjugates, and methods of treating cancer with such compounds and conjugates.

Abstract: A vane includes a pair of airfoils having a plurality of film cooling holes that extend through an exterior surface of the airfoils, the plurality of film cooling holes including at least a first subset of film cooling holes, wherein the first subset of film cooling holes break through the exterior surface at geometric coordinates set forth herein. Each of the geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.

Abstract: A vane assembly for a gas turbine engine includes an inner diameter platform, an outer diameter platform, and an airfoil shaped vane spanning from the inner diameter platform to the outer diameter platform. The airfoil shaped vane includes an internal cooling passage having a first inlet at the inner diameter platform and a second inlet at the outer diameter platform. An outer diameter platform cover is disposed radially outward of the outer diameter platform, relative to a radius of an arc defined by an arc of the outer diameter platform. The outer diameter platform includes at least one coolant cover inlet hole, the at least one coolant cover inlet hole being aligned with a corresponding second inlet.

Abstract: A computer-implemented system is configured to, responsive to failure of anonymity threshold criteria of a payment card transaction based dataset including a geographical region definition including solely a first geographical region, query a geographical information service for data indicative of geographical regions neighboring a first geographical region; iteratively query the payment card transaction based dataset using queries modifying the geographical region definition to include the first geographical region and one or more neighboring geographical regions; test returned results against the anonymity threshold criteria; and responsive to a positive test result, generating an approval indication for a data set.

Abstract: This application discloses anti-P-cadherin antibodies, antigen binding fragments thereof, and antibody drug conjugates of said antibodies or antigen binding fragments, particularly antibody drug conjugates comprising anti-P-cadherin antibodies conjugated to auristatin analogs. The invention also relates to methods of treating cancer using the antibody drug conjugates. Also disclosed herein are methods of making the antibodies, antigen binding fragments, and antibody drug conjugates, and methods of using the antibodies and antigen binding fragments as diagnostic reagents.

Abstract: A component for a gas turbine engine includes a trailing edge tip corner that at least partially defines a trailing edge cavity and a multiple of corner features within the trailing edge cavity, the multiple of corner features splayed along the trailing edge tip corner.

Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A main-body core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a platform. A skin core cooling passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The skin core cooling passage is divided by a wall into two discrete first and second skin core cooling passages each supplied with cooling fluid from opposing sides.

Abstract: An on-demand ecosystem (ODE) computing device for integrating on-demand delivery services with purchase transactions is provided. The ODE computing device receives item data from a registered merchant, and receives availability data from at least one registered carrier. The ODE computing device further provides a searchable interface that enables a user to search for item data from the registered merchant, and receives a selected item from the user via the searchable interface. The selected item is offered for sale by the registered merchant and includes a selected pick-up location. The selected item is to be delivered to the user from the selected pick-up location. The ODE computing device also allows either the registered merchant or the user to select one of the at least one registered carriers, and processes a payment transaction for the selected item including an item price and a delivery fee.

Abstract: A method for making an RF connector having an outer conductor and an inner conductor comprises pre-plating the outer conductor and the inner conductor of the connector with corrosion-resistant metallic material. The method also comprises injecting a material comprising polyimide/poly(silsesquioxane)-like nanocomposite material in a volume between the outer conductor and the inner conductor of the connector. The method further comprises heating the connector with the injected material to a temperature between about 150 C to about 380 C in a substantially dry nitrogen-based environment.

Abstract: A method of manufacturing a component for a gas turbine engine according to an exemplary aspect of the present disclosure includes forming the component with a first manufacturing technique to include a first cavity and a second cavity, and a microcircuit in fluid communication with the first cavity, the component including an outer wall and a ribbed portion or a bulged portion extending from the outer wall. The exemplary method includes forming a plunged hole with a second manufacturing technique different from the first manufacturing technique to intersect at least a portion of the microcircuit and extend into the ribbed portion or the bulged portion.

Abstract: A turbine vane assembly for a gas turbine engine is disclosed and includes an airfoil rotatable about a first axis transverse to an engine longitudinal axis. The airfoil includes an endwall and at least one protrusion disposed on the endwall configured for obstructing flow through a gap between the endwall and a static structure of the gas turbine engine.

Abstract: A co-doped optical fiber is provided having an attenuation of less than about 0.17 dB/km at a wavelength of 1550 nm. The fiber includes a core in the fiber having a graded refractive index profile with an alpha of greater than 5. The fiber also includes a cladding in the fiber that surrounds the core addition, the core includes silica that is co-doped with two or more halogens.

Abstract: Preparation of halogen-doped silica is described. The preparation includes doping silica with high halogen concentration and sintering halogen-doped silica to a closed-pore state. The sintering includes a high pressure sintering treatment and a low pressure sintering treatment. The high pressure sintering treatment is conducted in the presence of a high partial pressure of a gas-phase halogen doping precursor and densifies a silica soot body to a partially consolidated state. The low pressure sintering treatment is conducted in the presence of a low partial pressure of gas-phase halogen doping precursor and transforms a partially consolidated silica body to a closed-pore state. The product halogen-doped silica glass exhibits little foaming when heated to form fibers in a draw process or core canes in a redraw process.